A landing gear assembly is provided. The landing gear assembly includes a shock strut. The shock strut includes a shock strut cylinder and a shock strut piston slidably disposed within the shock strut cylinder. The landing gear assembly further includes a temperature control unit assembly disposed within the shock strut cylinder. The temperature control unit assembly is configured to, responsive to a temperature within the shock strut cylinder falling below a predetermined temperature, circulate heated fluid into a chamber of the shock strut cylinder to heat gas within the shock strut cylinder.

Provided is a single degree of freedom vibration isolator/damper system capable of overload protection. The vibration isolator reduces vibration transmitted to or from an isolated spacecraft component that generates micro-vibrations. The system isolates sensitive components and vibration sources from the spacecraft. The system may consist of a 1) first spring element in series with a first damper element; 2) a second spring element in parallel with the first spring element and first damper element; and 3) a support member that serves as the overload protection device.

A brace member includes a plastically deformable core member, a buckling restraining member through which the core member extends, a cap sleeve in which a first end portion of the core member and a first end portion of the buckling restraining member are disposed, a cap-sleeve crevice disposed on the cap sleeve so as to protrude toward a side opposite to a side on which the core member and the buckling restraining member are disposed, a reinforcing member in which a second end portion of the core member is disposed, and a reinforcing-member crevice disposed on the reinforcing member so as to protrude toward a side opposite to a side on which the core member is disposed. The reinforcing member surrounds a predetermined area of the buckling restraining member extending from a second end surface on the second side in the longitudinal direction.

A landing gear assembly is provided. The landing gear assembly includes a shock strut. The shock strut includes a shock strut cylinder and a shock strut piston slidably disposed within the shock strut cylinder. The landing gear assembly further includes a temperature control unit assembly disposed within the shock strut cylinder. The temperature control unit assembly is configured to, responsive to a temperature within the shock strut cylinder falling below a predetermined temperature, circulate heated fluid into a chamber of the shock strut cylinder to heat gas within the shock strut cylinder.

A metering unit is provided. The metering unit includes a metering pin analog and a translation shaft. The metering pin analog is configured to translate about the translation shaft in a first direction in response to a load pressure acting on an annular region of a bottom portion of the metering pin analog. The metering pin analog is configured to translate about the translation shaft in a second direction opposite the first direction in response to the load pressure ceasing.